% Top wall pressure, strong shock case % % H* = Throat height % P0 = Inlet total pressure % X/H* P/P0 -4.0350 0.86453 -3.3890 0.86384 -2.7550 0.87244 -2.2090 0.88115 -1.7060 0.83090 -1.0370 0.66588 -0.7490 0.59699 -0.4730 0.55834 -0.2880 0.54330 -0.1440 0.54508 0.0000 0.54043 0.1440 0.53573 0.2880 0.52434 0.4380 0.50580 0.5530 0.48147 0.6920 0.46319 0.8300 0.45295 0.9910 0.43316 1.1300 0.41817 1.2800 0.40506 1.4180 0.38850 1.5560 0.37769 1.7870 0.35200 2.0060 0.34714 2.2250 0.49682 2.4440 0.52137 2.8820 0.53745 3.3140 0.55328 3.9770 0.57845 4.4030 0.59600 5.1010 0.62331 5.7640 0.65214 6.3400 0.67350 6.9160 0.69371 7.4930 0.70504 8.0690 0.71503 8.6460 0.72268